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Publication numberUS2637076 A
Publication typeGrant
Publication dateMay 5, 1953
Filing dateOct 14, 1947
Priority dateOct 14, 1947
Publication numberUS 2637076 A, US 2637076A, US-A-2637076, US2637076 A, US2637076A
InventorsBolte Frank B
Original AssigneeNorth American Aviation Inc
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Reinforced canopy structure
US 2637076 A
Abstract  available in
Previous page
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Claims  available in
Description  (OCR text may contain errors)

May 5, 1953 F. B. BoLTE REINFoRcr-:D cANoPY STRUCTURE Filed Oct. 14, 1947 (7 /9 WWWW/MWW//W FRANK E. BOLT-E JNVENToR.

BY AQ ATTR/VEY Patented May 5, 1953 2,637,076 REINFORCED CANOPY STRUCTURE i Frank B. Bolte, Los Angeles, Calif., Aassigner to Noi-th American Aviation, Inc.

Application October 14, 1947, Serial No. 779,667

4 claims. (c1. .2o-4o) v This invention pertains to reinforcement of material and particularly of sheet material comosed of methyl methacrylate or like materials.

In the past considerable difficulty has been `experienced in obtaining plastic structures having sufficient strength to enable their use for airplane canopies and particularly in connection with pressurized cabins. Attempts have been made to reinforce these structures with structural metals. However, this has resulted in complicated structures having impaired pilot visibility and other undesirable features, including those arising because of differences in the coefficients of expansion of the two materials.

It is therefore an object of this invention to provide an integral reinforced plastic structure which is conveniently and economically formed and yet has high strength characteristics.

It is `another object of this invention to provide a reinforced plastic material which obtains a minimum impairment to visibility.

It is yet another object of this invention to provide a light weight relatively strong structure which is substantially homogeneous.

Other objects of invention will become apparent from the following description taken in connection with the accompanying drawings, in which Fig. l is an elevational View of a part of an airplane embodying the invention;

Fig. 2 is an enlarged perspective view of the underside of the canopy illustrated in Fig. l, but modified by having part of the tape unrecessed; and

Fig. 3 is a sectional View along the line Fig. 1.

Referring to the drawings, a structure l, such as an airplane or the like, is provided with a transparent canopy portion 2 suitably attached thereto. In the preferred embodiment of the in vention the transparent portion is formed of a relatively brittle shell substance 3, such as methyl methacrylate sheet material, stiffened by means of ribs 4 and spars vt, and reinforced with tapes 6, 1, 8, 9 and i0. The stifening ribs and spars may be formed of the same material as the shell and attached thereto by a monomer cement or the like. The tape may be composed of ductile plastic, suitably treated fabric, woven glass fiber, or equivalent substance. Preferably the tape is formed of a synthetic linear polyamide of the types obtained by polymerization of diamines with dibasic acids or their amide-forming derivatives.

The tape is rattached to the exterior or free face of the shell and to the interior or free face or faces of the stiifening elements. The exterior shell is preferably recessed for reception of the tapes 'l and 9, as illustrated in Fig. 3. Obviously, this is desirable when used in connection with airplane canopies, although it may be omitted where unnecessary. The spars and ribs on the interior are also recessed for the tapes 6 and 8, but `this may be omitted, if desired, as illustrated in Fig. r2. Tape I0 attached to the respective sides of the ribs and spars, servesto stiifen the resulting structure and strengthen the same somewhat.

In any event, the tapes are relatively thin and any recesses used in connection therewith are correspondingly shallow, resulting in a substantially flush surface. Where tapes cross, the recesses may be correspondingly milled or cut out to insure a resulting flush surface.

By selecting tape and plastic material composing the shell and stiffening ribs of substantially identical indices of refraction, there obtains a relatively transp-arent reinforcing structure.

The resulting structure is well adapted to withstand forces and pressures to which it will be subjected under normal conditions of operation, and particularly in connection with pressurized airplane cabins. There results a considerable saving in weight, an increased percentage of unobstructed vision, saving in production cost, and a shatter-resistant structure. Further, the arrangement is exible to the extent that the canopy may be design according to strength requirements, and particularly where it is desired to avoid shattering under conditions of operation where there is a possibility of it being struck by objects such as missiles. The reinforcing of the structure is particularly eiective to prevent disintegration of the canopy upon impact with an object. This obviously enhances the safety factor of the cabin and particularly when utilized in connection with pressurized cabins.

The reinforcing elements l0 may be omitted if so desired and the reinforcing tape on the exterior surface of the canopy may be placed at other positions than opposite the ribs and spars.

Although the invention has been described and illustrated in detail, it is to be clearly understood that the same is by way of illustration and example only and is not to be taken by way of limitation, the spirit and scope of this invention being limited only by the terms of the appended claims.

I claim:

1. The process of forming a reinforced plastic structure comprising bonding acrylic plastic stiffening elements to a shell similar in composition to said stiifening elements, recessing the free faces of said shell and said elements, and bonding in said recesses strips of plastic material relatively strong in tension impregnated with a monomer cement so as to assure integral and continuous bonding of said strips lto said shell and said stiiening elements, said recesses being formedv to a depth which is substantially the thickness of said strip of material whereby said strips of material are substantally flush With said shell and said stiffening element when received in said recesses.

2. An aircraft canopy comprising a rigid transparent plastic shell adapted to engage portions of an aircraft at the edges of said shell; a grid of rigid transparent plastic reinforcing elements complementary to the interior surface of said shell and bonded thereto; a exible transparent tension-resistingtape material bonded to the interior surface of said grid opposite said shell; additional tape material `oonded to said shell on the outer surface thereof in a grid pattern corresponding to and disposed opposite from said grid of rigid plastic, said tape thereby providing said canopy with tension-resisting properties.

3. An aircraft canopy comprising a rigid plastic transparent lamina forming a shell forattachment to an aircraft; a second reinforcing lamina of rigid transparent plastic material, said reinforcing lamina having 9, grid-like pattern the outer surface thereof being complementary to the interior surface of said shell and bonded thereto,.said reinforcing lamina having recessed portions on the surface thereof opposite from said shell; transparent tension-resisting tape received in said recesses and bonded to said reinforcing lamina; said shell being recessed opposite from said grid portions on the outer surface thereof; additional transparent tension-resisting tape received in said recesses of the shell and bonded thereto, said tape thereby providing said shell with a smooth exterior surface and tensionresisting properties.

4. An airplane canopy composed of a sheet of transparent material, a grid of ribs and spars integrally bonded to one surface of said sheet, and tension-resisting tape material integrally bonded to the other surface of said sheet and to said ribs and spars, said sheet material, ribs and spars, and tape material being transparent and having indices of refraction substantially the same.


References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 2,193,469 Ashton Mar. 12, 1940 2,230,393 Thomson Feb. 4, 1941 2,258,724 Wagner et al. Oct. 14, 1941 2,278,369 Hall Mar. 31, 1942 2,348,287 Fiekers May 9,1944 2,382,963 Dodge Aug. 21, 1945 2,385,684 Burtonfet al. Sept. 25, 1945 2,427,065 Nebesar Sept. 9, 1947 2,482,798 Rheinfrank, et al. Sept. 27, 1949 2,503,450 Nebesarl Apr. 11, 1950 2,511,168 Martin et al. June 13, 1950 OTHER REFERENCES Lucite methyl methacrylate resin manual, pp. 5l58, received Feb. 28, 1944, TP986.L9D9.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2193469 *Jan 21, 1939Mar 12, 1940Ashton Gladys BrookerFlexible, transparent covering and windshield
US2230393 *Mar 29, 1937Feb 4, 1941John B ThomsonAirplane structural element
US2258724 *Apr 25, 1938Oct 14, 1941Messerschmitt Boelkow BlohmFixation of window panes in aircraft
US2278369 *Jun 23, 1939Mar 31, 1942Pittsburgh Plate Glass CoLaminated glass
US2348287 *Mar 2, 1942May 9, 1944Baldwin Rubber CoMethod of forming composite articles
US2382963 *Jan 10, 1942Aug 21, 1945Libbey Owens Ford Glass CoWindshield or window construction
US2385684 *Sep 21, 1942Sep 25, 1945Douglas Aircraft Co IncPilot enclosure
US2427065 *Jun 6, 1944Sep 9, 1947Universal Moulded Products CorAirfoil structure
US2482798 *Feb 27, 1946Sep 27, 1949Norman Wayne AAircraft wing and method of manufacture
US2503450 *Mar 5, 1945Apr 11, 1950Universal Moulded Products CorAirfoil
US2511168 *Mar 30, 1946Jun 13, 1950Republic Aviat CorpConstruction and mounting of units of transparent synthetic resins
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US4964594 *Apr 11, 1988Oct 23, 1990Texstar, Inc.Blind fastener having special utility in the installation of transparencies in aircraft and the like
U.S. Classification428/38, 244/121, 156/298, 428/163, 156/212, 428/480
International ClassificationB64C1/00, B64C1/14
Cooperative ClassificationB64C1/1476
European ClassificationB64C1/14C